NASA/LANGLEY RC-08(B)3 AIRFOIL (rc08b3-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: NASA/LANGLEY RC-08(B)3 AIRFOIL (rc08b3-il) Reynolds number: 100,000 Max Cl/Cd: 45.51 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-rc08b3-il-100000.txt Download as CSV file: xf-rc08b3-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: NASA/LANGLEY RC-08(B)3 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.4681 0.10459 0.09980 -0.0101 1.0000 0.0976
-9.500 -0.4885 0.10112 0.09640 -0.0148 1.0000 0.0989
-9.250 -0.5094 0.09708 0.09243 -0.0200 1.0000 0.0992
-9.000 -0.4672 0.09204 0.08733 -0.0121 1.0000 0.1042
-8.750 -0.4676 0.08820 0.08351 -0.0129 1.0000 0.1079
-8.500 -0.4806 0.08394 0.07931 -0.0162 1.0000 0.1115
-8.250 -0.6062 0.08775 0.08293 -0.0166 1.0000 0.1009
-8.000 -0.5902 0.08458 0.07978 -0.0134 1.0000 0.1047
-7.750 -0.5902 0.08067 0.07586 -0.0156 1.0000 0.1091
-7.500 -0.6160 0.07769 0.07247 -0.0226 1.0000 0.1138
-7.250 -0.5920 0.07196 0.06704 -0.0196 1.0000 0.1170
-7.000 -0.5833 0.06871 0.06376 -0.0193 1.0000 0.1226
-6.750 -0.5851 0.06459 0.05944 -0.0209 1.0000 0.1301
-6.500 -0.5718 0.06147 0.05636 -0.0195 1.0000 0.1359
-6.250 -0.5676 0.05795 0.05267 -0.0194 1.0000 0.1457
-6.000 -0.5621 0.05531 0.04980 -0.0185 1.0000 0.1585
-5.750 -0.5538 0.05275 0.04715 -0.0168 1.0000 0.1728
-5.500 -0.5439 0.04991 0.04434 -0.0148 1.0000 0.1882
-5.250 -0.5341 0.04729 0.04176 -0.0126 1.0000 0.2043
-5.000 -0.5242 0.04488 0.03935 -0.0103 1.0000 0.2215
-4.500 -0.4764 0.03264 0.02455 -0.0062 1.0000 0.0836
-4.250 -0.4585 0.02947 0.02114 -0.0043 1.0000 0.0780
-4.000 -0.4371 0.02763 0.01847 -0.0014 1.0000 0.0717
-3.750 -0.4160 0.02582 0.01637 0.0001 1.0000 0.0713
-3.500 -0.3944 0.02347 0.01387 0.0011 1.0000 0.0740
-3.250 -0.3716 0.02208 0.01237 0.0022 1.0000 0.0766
-3.000 -0.3474 0.02074 0.01089 0.0033 1.0000 0.0783
-2.750 -0.3232 0.01960 0.00965 0.0044 1.0000 0.0817
-2.500 -0.2996 0.01846 0.00846 0.0054 1.0000 0.0872
-2.250 -0.0850 0.01313 0.00640 -0.0271 1.0000 1.0000
-2.000 -0.0717 0.01308 0.00618 -0.0248 1.0000 1.0000
-1.750 -0.0604 0.01308 0.00604 -0.0221 1.0000 1.0000
-1.500 -0.0503 0.01311 0.00595 -0.0192 1.0000 1.0000
-1.250 -0.0411 0.01318 0.00591 -0.0161 1.0000 1.0000
-1.000 -0.0322 0.01328 0.00590 -0.0130 1.0000 1.0000
-0.750 -0.0230 0.01341 0.00593 -0.0100 1.0000 1.0000
-0.500 -0.0133 0.01355 0.00599 -0.0071 1.0000 1.0000
-0.250 -0.0030 0.01372 0.00609 -0.0044 1.0000 1.0000
0.000 0.0080 0.01392 0.00622 -0.0019 1.0000 1.0000
0.250 0.0198 0.01414 0.00637 0.0005 1.0000 1.0000
0.500 0.0320 0.01439 0.00657 0.0026 1.0000 1.0000
0.750 0.0450 0.01467 0.00681 0.0046 1.0000 1.0000
1.000 0.0588 0.01499 0.00710 0.0063 1.0000 1.0000
1.250 0.1116 0.01539 0.00751 0.0004 0.9901 1.0000
1.500 0.1662 0.01576 0.00791 -0.0057 0.9790 1.0000
1.750 0.2232 0.01604 0.00827 -0.0122 0.9674 1.0000
2.000 0.2845 0.01618 0.00852 -0.0192 0.9552 1.0000
2.250 0.3462 0.01615 0.00865 -0.0260 0.9418 1.0000
2.500 0.4101 0.01590 0.00862 -0.0328 0.9271 1.0000
2.750 0.4563 0.01558 0.00849 -0.0356 0.9057 1.0000
3.000 0.5005 0.01507 0.00818 -0.0373 0.8842 1.0000
3.250 0.5283 0.01463 0.00786 -0.0355 0.8563 1.0000
3.500 0.5504 0.01415 0.00747 -0.0323 0.8230 1.0000
3.750 0.5698 0.01374 0.00709 -0.0286 0.7823 1.0000
4.000 0.5885 0.01350 0.00687 -0.0251 0.7302 1.0000
4.250 0.6076 0.01343 0.00668 -0.0219 0.6614 1.0000
4.500 0.6249 0.01373 0.00658 -0.0186 0.5534 1.0000
4.750 0.6373 0.01488 0.00681 -0.0151 0.3815 1.0000
5.000 0.6448 0.01729 0.00783 -0.0120 0.1850 1.0000
5.250 0.6599 0.01900 0.00907 -0.0099 0.1334 1.0000
5.500 0.6787 0.02032 0.01029 -0.0081 0.1123 1.0000
5.750 0.6989 0.02163 0.01152 -0.0066 0.0987 1.0000
6.000 0.7210 0.02339 0.01311 -0.0055 0.0909 1.0000
6.250 0.7444 0.02471 0.01463 -0.0043 0.0843 1.0000
6.500 0.7674 0.02683 0.01667 -0.0036 0.0779 1.0000
6.750 0.7905 0.02859 0.01881 -0.0022 0.0754 1.0000
7.000 0.8123 0.03080 0.02142 -0.0007 0.0734 1.0000
7.250 0.8319 0.03285 0.02377 0.0009 0.0701 1.0000
7.500 0.8508 0.03517 0.02620 0.0021 0.0671 1.0000
7.750 0.8669 0.03829 0.02976 0.0041 0.0670 1.0000
8.000 0.8737 0.04259 0.03499 0.0076 0.0699 1.0000
8.250 0.8785 0.04730 0.04028 0.0104 0.0728 1.0000
8.500 0.8813 0.05175 0.04514 0.0128 0.0744 1.0000
8.750 0.8837 0.05636 0.05003 0.0147 0.0761 1.0000
9.500 0.7393 0.09258 0.08753 0.0002 0.1668 1.0000
9.750 0.7882 0.09379 0.08882 0.0098 0.1601 1.0000
10.000 0.7280 0.10215 0.09701 -0.0034 0.1563 1.0000
10.250 0.7274 0.10620 0.10105 -0.0044 0.1504 1.0000
10.500 0.7424 0.11009 0.10496 -0.0017 0.1456 1.0000
10.750 0.7157 0.11564 0.11039 -0.0086 0.1400 1.0000
11.000 0.5922 0.11161 0.10660 0.0041 0.1482 1.0000
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Polar data table (+)
Polar graphs
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